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Pratt and Whitney T34

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Pratt & Whitney T34

The Pratt & Whitney T34 (company designation PT2) was an axial flow turboprop engine designed and built by Pratt & Whitney. Its model name was Turbo-Wasp.

Contents

Design and development

In 1945 the United States Navy funded the development of a turboprop engine. The T34 was produced from 1951 to 1960, but never used in U.S. Navy aircraft production.

The YT34 engine with three wide-bladed propellers was made for two Navy Lockheed R7V-2 Constellation(C-121s) variants, for testing. Flight tests were on 1 September 1954.

In September 1950, a testbed Boeing B-17 Flying Fortress flew with a T34 turboprop mounted in the nose of the bomber. The first application for the T34 was the Boeing YC-97J Stratofreighter, which later became the Aero Spacelines Super Guppy. The next application for the engine was the Douglas C-133 Cargomaster.

Variants

YT34-P-5
5,229 hp (3,900 kW; 5,200 shp)
YT34-P-12A
5,500 hp (4,101.35 kW)
T34-P-3
6,000 hp (4469 kW)
T34-P-6
5,531 hp (4,120 kW; 5,500 shp)
T34-P-7W
7,100 hp (5288 kW) w/water injection
T34-P-9W
7,500 hp (5586 kW) w/water injection
PT2F-1
5,500 hp (4,101.35 kW); unbuilt civilian version planned to power the Lockheed L-1249B.
PT2G-3
5,600 hp (4,200 kW); unbuilt civilian version planned to power the Lockheed L-1449 and possibly the L-1549.

Applications

  • Aero Spacelines Super Guppy
  • Boeing YC-97J Stratofreighter (YT34-P-5)
  • Lockheed R7V-2 Constellation (YT34-P-12A)
  • Lockheed YC-121F Constellation (T34-P-6)
  • Douglas YC-124B Globemaster II
  • Douglas C-133 Cargomaster
  • Engines on display

  • T34-P-3: National Air and Space Museum (NASM)
  • T34-P-6: Travis Heritage Center at Travis AFB in Fairfield, CA
  • T34-P-7W: NASM
  • T34-P-7WA: Pacific Coast Air Museum (PCAM)
  • Specifications (T34-P3)

    Data from Jane's All The World's Aircraft 1961–62

    General characteristics

  • Type: Turboprop
  • Length: 156.8 in (3,983 mm)
  • Diameter: 33.75 in (857 mm)
  • Dry weight: 2,590 lb (1,175 kg)
  • Components

  • Compressor: 13-stage axial compressor
  • Combustors: annular combustion chamber with eight flame tubes
  • Turbine: three-stage axial-flow
  • Fuel type: JP-4
  • Oil system: closed circuit
  • Performance

  • Maximum power output: 5,500 shp (4,103 kW) plus 1,1250 lbf (5.57 kN) thrust, 6,000 ehp (4,476 kW) (take-off power)
  • Overall pressure ratio: 6.7:1
  • Power-to-weight ratio: 2.32 ehp/lb
  • References

    Pratt & Whitney T34 Wikipedia


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